CN218806485U - Concentrated force diffusion angle box of composite beam - Google Patents
Concentrated force diffusion angle box of composite beam Download PDFInfo
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- CN218806485U CN218806485U CN202222703230.7U CN202222703230U CN218806485U CN 218806485 U CN218806485 U CN 218806485U CN 202222703230 U CN202222703230 U CN 202222703230U CN 218806485 U CN218806485 U CN 218806485U
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- edge strip
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- web plate
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The application belongs to the field of aircraft structure design, and particularly relates to a concentrated force diffusion angle box of a composite beam, which is provided with an upper edge strip, a lower edge strip and a web plate for connecting the upper edge strip and the lower edge strip, wherein one side of the concentrated force diffusion angle box provided with the upper edge strip and the lower edge strip is an inner side, a central circular tube is arranged at the inner side of the web plate, the central circular tube is provided with a central hole, and the central hole penetrates through the web plate; the upper edge strip, the lower edge strip and the web plate are provided with mounting through holes; the composite beam is provided with a beam upper edge strip, a beam lower edge strip and a beam web plate, and the composite beam is provided with a beam mounting hole corresponding to the implementation mounting through hole; the beam web plate is provided with a through hole corresponding to the central hole; the bolt is used for attaching and installing the concentrated force diffusion angle box on the composite beam through the installation through hole and the beam installation hole; the detachable connection of the wing beam and other large airplane components is realized.
Description
Technical Field
The application belongs to the field of aircraft structural design, in particular to a concentrated force diffusion corner box of a composite beam.
Background
The connection of fuselage frame and wing spar for evenly transmitting load, can use bolt crowd to connect, but this kind of connected mode is usually undetachable connection, can't realize the quick assembly disassembly of wing and fuselage.
The thickness of the general web is far less than that of the flange strip, the general corner box is only connected with the web and cannot bear larger force vertical to the web, the composite beam has poorer capability of bearing external force, and the web needs to be locally thickened to cause weight increase.
The manufacturing precision of the composite material part is poor, and the matching precision of the composite material beam and other large parts is difficult to guarantee.
SUMMERY OF THE UTILITY MODEL
In order to solve the above problems, the present application provides a concentrated force diffusion corner box of a composite beam,
the concentrated force diffusion angle box is provided with an upper edge strip, a lower edge strip and a web plate connecting the upper edge strip and the lower edge strip, one side of the concentrated force diffusion angle box, which is provided with the upper edge strip and the lower edge strip, is an inner side, the inner side of the web plate is provided with a central circular tube, the central circular tube is provided with a central hole, and the central hole penetrates through the web plate; the upper edge strip, the lower edge strip and the web plate are provided with mounting through holes;
the composite beam is provided with a beam upper edge strip, a beam lower edge strip and a beam web plate, and the composite beam is provided with a beam mounting hole corresponding to the implementation mounting through hole; the beam web plate is provided with a through hole corresponding to the central hole;
the bolt enables the concentrated force diffusion corner box to be attached and installed on the composite beam through the installation through hole and the beam installation hole;
and the large bolt penetrates through the central hole and the beam web plate to be connected with the large part of the airplane.
Preferably, the central circular tube is connected with the web plate, the upper edge strip and the lower edge strip through vertical ribs and inclined ribs.
Preferably, the central circular tube extends to the outer side of the web plate to form a cylindrical protrusion, and the cylindrical protrusion is inserted into the through hole.
Preferably, the length of the cylindrical protrusion is greater than the thickness of the through hole of the web plate, the part of the cylindrical protrusion inserted into the through hole and beyond the through hole is sleeved with the gasket, the thickness of the gasket is the same as the length of the cylindrical protrusion, and the end face of the gasket and the end face of the cylindrical protrusion are attached to the surface of the large part of the airplane.
Preferably, the upper edge strip and the lower edge strip are in a stepped shape and have variable thicknesses, and the thicknesses of the upper edge strip and the lower edge strip gradually become thicker as the upper edge strip and the lower edge strip approach the central circular tube, so that uniform diffusion and weight reduction of loads are facilitated.
Preferably, a gap is formed between the concentrated force diffusion angle box and the composite beam, and the gap is filled with structural adhesive.
Preferably, the thickness of the glue layer of the structural glue is 0.3-2.5mm.
This application has realized the dismantled connection of wing spar and other big parts of aircraft.
The thickness of the flange strip is usually much greater than that of the web, and the typical corner box is only connected to the web and can only withstand small forces perpendicular to the web. The angle box is directly connected with the beam edge strip, so that large force perpendicular to a beam web plate can be directly transmitted to the thick beam edge strip, and external force of a bearing surface of a composite part is avoided.
The manufacturing precision of the composite part is poor, the composite part is easy to be out of tolerance as a matching surface, and the metal part protrudes out of the composite beam through innovative design to form a high-precision matching surface with other large parts of the airplane.
Through the innovative design of the diagonal box, the concentrated force acting on the diagonal box is uniformly diffused to the beam edge strips and the beam web plates.
The diffusion angle box is connected with the wing beam by using a mixed connection mode of gluing and bolt connection, the glue layer can be used for compensating an assembly gap, the position precision of a center hole of the angle box is guaranteed, the glue layer is subjected to shearing, and the bolt can prevent the glue layer from being peeled off and pulled.
Drawings
FIG. 1 is a schematic view of a preferred embodiment of the present application with a force concentrating and diffusing corner box nested within a composite beam;
FIG. 2 is a schematic view of a preferred embodiment of the present application with a gasket on the back of a composite beam;
FIG. 3 is an exploded view of a preferred embodiment focused force diffusing corner box assembly of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are implementations that are part of this application and not all implementations. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides a concentrated force diffusion corner box of a composite beam,
the concentrated force diffusion angle box 101 is provided with an upper edge strip, a lower edge strip and a web plate connecting the upper edge strip and the lower edge strip, one side of the concentrated force diffusion angle box 101, which is provided with the upper edge strip and the lower edge strip, is an inner side, the inner side of the web plate is provided with a central circular tube, the central circular tube is provided with a central hole, and the central hole penetrates through the web plate; the upper edge strip, the lower edge strip and the web plate are provided with mounting through holes;
the composite beam 2 is provided with a beam upper edge strip, a beam lower edge strip and a beam web plate, and the composite beam 2 is provided with a beam mounting hole corresponding to the implementation mounting through hole; the beam web plate is provided with a through hole corresponding to the central hole;
the bolt is used for attaching and installing the concentrated force diffusion angle box 101 on the composite beam 2 through the installation through hole and the beam installation hole;
and the large bolt penetrates through the central hole and the beam web plate to be connected with the large part of the airplane.
A large detachable bolt penetrates through the central circular tube to be connected with other large components, so that a concentrated force acts on the central circular tube, and the concentrated force is uniformly diffused to the composite beam through the corner box. The concentrated force can be divided into two components, perpendicular and parallel to the axis of the central tube. For the force vertical to the axis of the central circular tube, most of the force is transmitted to the web plate through the connection of the web plate of the concentrated force diffusion angle box 101 and the web plate, so that the web plate is sheared, and the small part of the force is transmitted to the beam through the vertical ribs and the inclined ribs of the concentrated force diffusion angle box 101; for the force parallel to the axis of the central circular tube, most of the force is transmitted to the beam edge strip through the studs of the concentrated force diffusion angle box 101 to become the in-plane force of the beam edge strip, and the small part of the force is transmitted to the beam web through the connection of the web of the concentrated force diffusion angle box 101 and the beam web; after the concentrated force is diffused through the concentrated force diffusion corner box 101, most of the force is converted into the in-plane force of the composite beam, so that the composite part is prevented from bearing the in-plane force.
Preferably, the central circular tube is connected with the web plate, the upper edge strip and the lower edge strip through vertical ribs and inclined ribs.
Preferably, the central circular tube extends to the outer side of the web plate to form a cylindrical protrusion, and the cylindrical protrusion is inserted into the through hole.
Preferably, the length of the cylindrical protrusion is greater than the thickness of the through hole of the web plate of the beam, the part of the cylindrical protrusion inserted into the through hole and exceeding the through hole is sleeved with the gasket 102, the thickness of the gasket 102 is the same as the exceeding length of the cylindrical protrusion, the exceeding length is 2mm, the gasket 102 and the end face of the cylindrical protrusion are attached to the surface of the large part of the airplane, because the concentrated force diffusion angle box 101 and the gasket are both metal parts, the manufacturing precision is much higher than that of a composite beam, the metal end face can be filed in the assembly process, and the assembly precision of the beam and other large parts can be guaranteed.
Preferably, the upper edge strip and the lower edge strip are in a stepped shape and have variable thicknesses, and the thicknesses of the upper edge strip and the lower edge strip gradually become thicker as the upper edge strip and the lower edge strip approach the central circular tube, so that uniform diffusion and weight reduction of loads are facilitated.
Preferably, a gap is formed between the concentrated force diffusion corner box 101 and the composite beam 2, and the gap is filled with structural adhesive.
Preferably, the thickness of the adhesive layer of the structural adhesive is 0.3-2.5mm, the adhesive layer mainly bears shearing force and pressure, the bolt is used for bearing tensile force and can be used as a safety measure after the adhesive layer fails, and the safety margin of connection of a key structure is improved.
The detachable connection of the wing beam and other large parts of the airplane, such as the airplane body and the landing gear, is realized.
The thickness of the cap is generally much greater than that of the web, and the conventional corner box is connected to the web only, and can only withstand small forces perpendicular to the web. The angle box is directly connected with the beam edge strip, so that larger force perpendicular to a beam web plate can be directly transmitted to the thicker beam edge strip, and the external force of a bearing surface of a composite part is avoided.
The manufacturing precision of the composite part is poor, the composite part is easy to be out of tolerance as a matching surface, and the metal part protrudes out of the composite beam through innovative design to form a high-precision matching surface with other large parts of the airplane.
Through the innovative design of the diagonal box, the concentrated force acting on the diagonal box is uniformly diffused to the beam edge strips and the beam web plates.
The diffusion angle box is connected with the wing beam by using a mixed connection mode of gluing and bolt connection, the glue layer can be used for compensating an assembly gap, the position precision of a center hole of the angle box is guaranteed, the glue layer is subjected to shearing, and the bolt can prevent the glue layer from being peeled off and pulled.
One embodiment is as follows: the butt joint of the wing body of an unmanned transport plane is a designed separating surface and is required to be detachable, the wing composite beam is connected with the plane through the concentrated force diffusion angle box, a phi 20 large bolt penetrates through the central circular tube and the plane frame, the plane frame is tightly attached to two end surfaces of the central circular tube of the concentrated force diffusion angle box, and in order to ensure the relative positions of the plane and the wing, two end surfaces and gaskets of the central circular tube of the concentrated force diffusion angle box need to be filed and repaired. The large concentrated loads transmitted from the fuselage are successfully diffused to the composite material beams of the wing through the concentrated force diffusion angle box.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A concentrated force diffusion corner box of a composite beam is characterized in that,
the concentrated force diffusion angle box (101) is provided with an upper edge strip, a lower edge strip and a web plate connecting the upper edge strip and the lower edge strip, one side of the concentrated force diffusion angle box (101) provided with the upper edge strip and the lower edge strip is an inner side, a central circular tube is arranged on the inner side of the web plate, the central circular tube is provided with a central hole, and the central hole penetrates through the web plate; the upper edge strip, the lower edge strip and the web plate are provided with mounting through holes;
the composite beam (2) is provided with an upper beam edge strip, a lower beam edge strip and a beam web plate, and the composite beam (2) is provided with a beam mounting hole corresponding to the implementation mounting through hole; the beam web plate is provided with a through hole corresponding to the central hole;
the bolt enables the concentrated force diffusion corner box (101) to be attached and installed on the composite beam (2) through the installation through hole and the beam installation hole;
and the large bolt penetrates through the central hole and the beam web plate to be connected with the large part of the airplane.
2. The composite beam concentrating force diffusing corner box according to claim 1, wherein said central circular tube is connected to the web, the upper and lower beads by studs and rakes.
3. The concentrated force diffusion corner box of a composite beam as defined in claim 1, wherein said central circular tube extends outward of said web to form a cylindrical protrusion, said cylindrical protrusion being inserted into said through hole.
4. The concentrated force diffusion corner box of a composite beam as claimed in claim 3, wherein the length of the cylindrical protrusion is greater than the thickness of the through hole of the web, the gasket (102) is sleeved on the portion of the cylindrical protrusion inserted into the through hole, and the thickness of the gasket (102) is the same as the length of the cylindrical protrusion, so that the end faces of the gasket (102) and the cylindrical protrusion are attached to the surface of the large part of the airplane.
5. The concentrated force spreading corner box of a composite beam as claimed in claim 1, wherein the upper and lower rims are stepped to become thicker, and the thickness of the upper and lower rims becomes thicker as approaching the central circular tube, thereby facilitating uniform spreading and weight reduction of the load.
6. The concentrated force diffusion corner box of composite beam according to claim 1, characterized in that there is a gap between the concentrated force diffusion corner box (101) and the composite beam (2), and the gap is filled with structural glue.
7. The composite beam concentrated force diffusion corner box of claim 1, wherein the glue layer of the structural glue has a thickness of 0.3-2.5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222703230.7U CN218806485U (en) | 2022-10-12 | 2022-10-12 | Concentrated force diffusion angle box of composite beam |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222703230.7U CN218806485U (en) | 2022-10-12 | 2022-10-12 | Concentrated force diffusion angle box of composite beam |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218806485U true CN218806485U (en) | 2023-04-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222703230.7U Active CN218806485U (en) | 2022-10-12 | 2022-10-12 | Concentrated force diffusion angle box of composite beam |
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| Country | Link |
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| CN (1) | CN218806485U (en) |
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2022
- 2022-10-12 CN CN202222703230.7U patent/CN218806485U/en active Active
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